33results about How to "Stable and reliable flight" patented technology

The invention relates to an efficient drone for logistics distribution and with flight stability. The efficient drone comprises a main drone body, several conveying devices and several flight mechanisms, the conveying devices comprise adjusting mechanisms, adjusting plates and conveying mechanisms, the adjusting mechanisms comprise connecting rods, rotary plates, rotary assemblies and translationassemblies, and the translation assemblies comprise first motors, bearings, lead screws and translation blocks; the conveying mechanisms comprise detection assemblies, detection plates, lifting assemblies, lifting plates, air pumps and several fixing assemblies, and the fixing assemblies comprise air cylinders, pistons, vertical plates, bottom plates and fixing units. According to the efficient drone for logistics distribution and with flight stability, loading and unloading of goods are facilitated through the conveying mechanisms, the efficient drone conveniently carries multiple goods for conveying at a time, and the logistics distribution efficiency is improved; besides, by detecting the weight of the goods, the adjusting mechanisms control the positions of adjusting plates, thus the gravity center of the drone is adjusted to be located on the central axis of the main drone body, steady flight of the drone is facilitated, and the practicability of the drone is improved.

The invention discloses a wiring method for an airborne cable device frame of an unmanned aerial vehicle. By stereoscopic space wiring, most of instrument devices and control boxes of the unmanned aerial vehicle are mounted on the double-layered device frame, the airborne cable device frame is divided into four spaces, and the spaces are connected through a cable bundle. The cable bundle of the device frame is an integral cable set and is totally provided with 34 connectors. The device frame is divided into an upper layer and a lower layer, is divided into four areas A, B,C,D from top to bottom according to a principle of heading from front to back and from left to right, coordinates are sequentially set as locating points, namely, 25 locating points, and each locating point is provided with a fixing clip used for fixing wire harness. Due to the fact that by stereoscopic space wiring process, most of the instrument devices and the control boxes of the unmanned aerial vehicle are mounted on the double-layered device frame, the airborne cable device frame has four spaces, and the spaces are effectively connected through a complete cable bundle, normal operation of devices is achieved, the method is reasonable in wiring path and process and small in space occupation, wiring is easy, and reliable flight of the unmanned aerial vehicle is guaranteed.

The invention belongs to the technical field of drone battery protection, and discloses a battery thermal insulation heating control system and method in a low temperature environment, a drone and a medium, and a battery thermal insulation heating transport box provides a storage and transportation box for drone batteries; The intelligent battery temperature control system is integrated in the battery thermal insulation heating transport box for temperature management involved in the intelligent battery of the drone; the drone low temperature algorithm system is integrated in the battery thermal insulation heating transport box for realizing The flight strategy adopted by the drone when it detects that the outside is in a low temperature environment. The invention solves the lossless heat preservation and heating of the battery through the battery heat preservation and heating transportation box, uses the battery temperature control system to ensure the real-time monitoring of the battery temperature, and ensures the battery safety state before take-off through the unmanned aerial vehicle low temperature algorithm, and realizes the unmanned aerial vehicle. reliable flight in low temperature environment. The invention can ensure the safety and reliability of unmanned aerial vehicle flight under low temperature environment.

The invention discloses an unmanned aerial vehicle self-navigation and positioning method based on multi-model distributed filtration and aims to reduce the calculation complexity of the unmanned aerial vehicle self-navigation and positioning method, meet a requirement of an embedded processor on real-time processing, guarantee stable control on an unmanned aerial vehicle and also ensure self-navigation and positioning of the unmanned aerial vehicle under a condition that a satellite navigation positioning system is unavailable within short time or long time. By the virtue of the unmanned aerial vehicle self-navigation and positioning method, measured values of motion of the unmanned aerial vehicle are obtained through different measurement systems and different sensors by constructing different orders of system state equations for estimating multi-mode distributed filtration states; a distributed filtration method is adopted to estimate and compensate an error of a low-cost inertial navigation system, so that continuous and reliable navigation and positioning information can be supplied to the unmanned aerial vehicle. The unmanned aerial vehicle self-navigation and positioning method disclosed by the invention can continuously and stably supply precise navigation and positioning information to an unmanned aerial vehicle control system for a long time.

The invention discloses a rotorless remote-controlled aircraft, which belongs to the field of jet aircraft. The rotorless remote control aircraft of the present invention comprises an annular blast cavity, a turbine blow mechanism and a bin body, the bin body is fixed in the middle of the annular blast cavity, an annular cavity is arranged in the annular blast cavity, and an annular cavity is arranged in the annular cavity. There are at least three sets of partitions that equally divide the annular cavity into mutually independent areas, and the middle part of each independent area of ​​the annular cavity is correspondingly provided with a set of evenly arranged on the outer wall of the annular blast cavity for blowing the air to the annular A turbine blowing mechanism that blows air into the cavity. The annular blowing cavity is provided with a circle of air jets that can jet downward to provide lift. The annular cavity is also equipped with a steering mechanism that can drive the diaphragm to rotate to change the direction of the jet. . The aircraft of the present invention has simple and compact structure, strong flight power, stable and reliable flight, simple and convenient control, and strong battery life; at the same time, the aircraft is safer to use and meets the needs of young children.

The present invention discloses a UAV uplink scheduling method based on TD‑LTE technology oriented to QoS guarantee of information flow: an information flow generation module, a classification mapping module, a scheduling module and a channel state detection module at the UAV communication terminal , and the wireless resource configuration module, the channel state detection module and the information flow recovery module at the eNodeB are cooperatively implemented under the control of various signaling. The present invention adopts the 4G communication network TD-LTE, and proposes a UAV information flow classification mapping method and scheduling algorithm, which can provide differentiated transmission services for various types of information sent back to the control management center by the UAV during flight , to provide an effective link guarantee for the reliable flight of UAVs and the acquisition of high-quality collection information.

The invention discloses a power transmission line inspection-based multi-rotor unmanned aerial vehicle inspection operation simulation training system. The power transmission line inspection-based multi-rotor unmanned aerial vehicle inspection operation simulation training system is established by using the virtual reality technology. The system includes a training host as well as an unmanned aerial vehicle remote controller, a keyboard, a mouse, a display, and a virtual reality helmet which are all connected with the training host in a wireless or wired manner; the training host is the mastercontrol device of the system, and is provided with a virtual unmanned aerial vehicle flight control simulation unit, a virtual unmanned aerial vehicle flight simulation unit, a training evaluation management unit, a defect location and identification unit, a database unit and a background management unit; the unmanned aerial vehicle remote controller, the keyboard and the mouse are all the inputdevices of the system; and the display and virtual reality helmet are the display devices of the system. The simulation training system of the present invention can be used not only to improve the unmanned aerial vehicle inspection operation control skills of operators and but also to prevent unnecessary loss of personnel, grid lines, or unmanned aerial vehicles due to the improper handling of special circumstances.

The invention relates to a flying-saucer-type land-air amphibious bamboo cutting machine, and belongs to the technical field of agricultural machinery. The flying-saucer-type land-air amphibious bamboo cutting machine comprises a rack, the top of the rack is provided with a cab, and a start button connected with a vertical shaft engine is arranged in the cab; the rack is provided with the vertical shaft engine and a dual-clutch transmission which are connected through a shaft, a back drive shaft of the dual-clutch transmission is connected with a back rotary wing drive shaft through a transmission part, the two ends of the back rotary wing drive shaft are connected with a back rotary wing and a back wheel drive shaft through clutches respectively, the back wheel drive shaft drives back walking wheels to walk, a front drive shaft of the dual-clutch transmission is connected with a front transmission shaft through a transmission part, the front transmission shaft is connected with a front rotary wing, a disc saw and a front wheel drive shaft through the matched clutches respectively, and the front wheel drive shaft drives front walking wheels to walk. The flying-saucer-type land-air amphibious bamboo cutting machine is simple in structure, safe and efficient, can walk on the flat land and also can fly across obstacles such as a ravine and a mountain slope through the rotary wings, continuous and automatic bamboo cutting is achieved, and the requirements of bamboo cutting in a hilly and mountains region can be well met.

The invention discloses an unmanned aerial vehicle autonomous navigation positioning method with assistance of visual information. The positioning method aims at providing accurate unmanned aerial vehicle navigation positioning information by making use of a visual sensor and corresponding visual ranging algorithm. In the method, speed and position information of the unmanned aerial vehicle are calculated through a combined visual ranging algorithm, and are used for assisting inertial navigation positioning. When a GNSS (Global Navigation Satellite System) signal is available, inertial navigation system error is corrected through inertial navigation / GNSS combined navigation, and a visual ranging evaluation criterion is established; when the GNSS signal is unavailable, the visual ranging evaluation criterion is used for evaluating the visual ranging result obtained by the combined visual ranging algorithm, error of a inertial navigation system is estimated and compensated with the visual ranging result and the visual ranging evaluation result, and thus, continuous and reliable navigation positioning information is provided for the unmanned aerial vehicle. The method provided by the invention can continuously and steadily provide accurate navigation positioning information for an unmanned aerial vehicle control system for long time.

The invention provides an attitude control method adaptive to a long-time out-of-control state and belongs to the technical field of carrier rocket control. The method comprises the steps that after starting control, the angular speed is reduced through angular speed control; to ensure that the angular speed of three channels is reduced rapidly, a spray pipe continuous opening working mode is adopted, corresponding spray pipes are opened for the three channels according to the direction of the angular speed until the angular speed is reduced to 0, and when the last angular speed of the three channels is reduced to the level near 0, the three channels are switched to control based on attitude angular deviation at the same time. In the control process of attitude angular deviation, the angular deviation of attitude control under a rocket system is calculated according to a program quaternion and an actual quaternion. By means of the attitude control method adaptive to the long-time out-of-control state, the attitude that an orbit transfer vehicle deviates from a standard trajectory can be suppressed quickly, and it is ensured that an air vehicle flies stably and reliably under full-space attitude orientation.

The invention relates to a static test device and method for a power element of a high-altitude full-electric UAV, and belongs to the technical field of performance test of small UAV. The test deviceis mainly composed of a simulated high-altitude pressure chamber and a power element performance test platform. The simulated high-altitude pressure chamber simulates atmospheric pressures in different flight high-altitude environments and realizes axial positioning of the power element performance test platform, and the power element performance test platform measures parameters including a thrust of a power system, the input electric energy power, a rotating speed of a blade and the motor temperature comprehensively. The method based on the test device can be used to measure the performanceparameters of the power elements of the UAV in the simulated high-altitude flight environment accurately, static test of the power elements is effectively combined with the test environment, the method and device are adapted to performance test of different parameter function parts, and the technical problem in evaluating performances of the power system in different flight environments in the research process of the high-altitude full-electric VAV is solved.